Boundary-Layer, Pressure, and Temperature Distribution Studies on Several Isentropic Compression Surfaces at Mach Numbers from 4 to 8

摘要

Boundary-layer, pressure, and temperature measurements were obtained on the generating cylinder and isentropic compression surface of several axisymmetric hypersonic inlet configurations at supersonic and hypersonic Mach numbers. Boundary-layer surveys were performed at selected stations on uncooled Mach 5, 6, and 10 inlets and a cooled Mach 8 inlet. Model surface temperatures and pressures were obtained at several Mach numbers on all configurations. Steady-state heat transfer data were obtained on the Mach 8 inlet at several model wall temperatures. Selected results from the tests are presented. (Author)